Aeroplane-controlling mechanism



z m-wa w. H. GETTEMY, 1a. AER'OPLVANECONTROLLING MECHANISM.

APPLICATION FILED DEC. 3. 1917.

1,306,002. Patented June 10, 1919.

2 SHEETS-SHEET1- 244. AERONAUTICS W. H. GETTEMY. JR.

AEROPLANE CONTROLLING MECHANISM.

APPLICATION FILED DEC- 3,1917- 1 ,306,002. Patented June 10, 1919.

2 SHEETS-SHEET 2- 244. AERONAUTICS WILLIAM H. GETTEMY, J 3., OF ROCKFORD, IOWA.

AEROPLANE-CON'IROLLING MECHANISM.

Specification of Letters Patent.

Patented June 10, 1919.

Application filed December 3, 1917. Serial No. 205,128.

To all whom it may concern:

Be it known that I, \VILLIAM H. GETTEMY, J r., a citizen of the United States, residing at Rockford, in the county of Floyd, State of Iowa, have invented certain new and useful Improvements in Aeroplane-Controlling Mechanisms; and I do hereby declare the following to be a full, clear, and exact description of the invention, such as will on able others skilled in the art to which it appertains to make and use the same.

This invention relates to improvements in aeroplanes and particularly to controlling mechanisms therefor.

One object of the present invention is to provide a mechanism whereby the ascending and descending movements of the aeroplane can be quickly and safely controlled.

Another object is to provide an aeroplane in which the sustaining planes are adapted to be tilted downwardly or upwardly, to govern the rising or descending of the aeroplane, while the propeller and engine remain in a horizontal position.

Other objects and advantages will be apparent from the following description when taken in connection with the accompanying drawing.

In the drawing:

Figure 1 is a side elevation of an aeroplane made in accordance with my invention.

Fig. 2 is a rear elevation of the same.

Fig. 3 is a side elevation of the aeroplane showing the planes tilted for ascending.

Fig. 4 is a side elevation of the areoplane in the position for descending.

Fig. 5 is a vertical sectional view taken on the line 5-5 of Fig. 2.

Fig. 6 is a horizontal sectional view taken on the line 66 of Fig. 2.

Referring particularly to the accompanying drawings, 10 represents the planes of the aeroplane, which are pivotally connected, at their inner ends, to the forward end portion of the fuselage or body of the machine, said fuselage being represented .by the character 12'. An engine 13 is mounted in the forward end of the fuselage and has the shaft 14 for driving the propeller 14:. At

the rear of the fuselage there is mounted the guidlng rudder 12".

Mounted on the pivot members 17 and 17 1 in the fuselage, at opposite sides of the seat, are the levers l8 and 21. The lever 18 is pivotally connected at 19, to one side of a yoke member 12 which has the upper ends of its arms secured to the inner end portions of the planes 10, and extends downwardly and transversely beneath the fuselage, as clearly shown in the drawing, and especially in Fig. 2. The lever 21 is pivotally connected to the other side of the yoke member, at 22. The other ends of the levers 18 and 22 are disposed within convenient reach of the operator, where they are provided. with the hand grips 23.

When the lever 18 is moved downwardly the yoke member will be depressed and cause the downward swinging movement of theplanes, and when the lever 21 is moved the planes will be swung upwardly. Thus the planes are capable of movement to control the upward and downward movement of the machine, while the body or fuselage remains in a horizontal plane. Thus the whole machine is not moved at various angles with respect to the ground, as is the usual case Where ailerons or other such tilting surfaces are employed.

What is claimed is:

In an areoplane controlling mechanism, the combination with a fuselage, sustaining planes pivotally mounted at their forward edges to the forward end of the fuselage and movable vertically, a yoke member extending beneath the fuselage and connected at its ends to the sustaining planes whereby said planes will move in unison, levers pivotally mounted in the fuselage, and links connected to the levers and to the inner ends of the sustaining planes.

In testimony whereof, I aflix my signature in the presence of two witnesses.

WILLIAM H. GETTEMY, JR. Witnesses:

PHILIP GREENE, GEORGE H. HUBER.

Copies of this patent may be obtained for five cents each, by addressing the Commissioner of Patents,

- Washington, D. G. 

